摘要
通常的立式贮存条件下固体火箭发动机药柱的结构完整性研究并没有考虑界面损伤。本文以某型固体火箭发动机模型为例,在推进剂与绝热层之间设置粘接接触,对比分析了有无界面损伤时发动机在固化降温、充气内压和重力载荷的联合作用下的应力特性。结果表明:界面损伤的存在导致推进剂/绝热层界面这个薄弱环节更危险;考虑界面损伤时,靠近人工脱粘层根部位应力随着充气内压增大呈先增大后减小趋势;在充气内压逐渐增大过程中,推进剂药柱与绝热层之间考虑界面损伤时,推进剂药柱的危险点由靠近人工脱粘层根部部位变为垂直于轴向的初始点。
Common structural integrity studies of vertical storage solid rocket motor grains lack the consideration of interface damage. Based on a certain solid rocket motor model,the adhesive contact is set between the propellant and the thermal insulation layer to consider the interface damage. The stress characteristics of the motor under the combination of solidification and cooling,inflation pressure and gravity load are compared and analyzed with or without interface damage.The results show that the existence of interface damage makes the weak link of the propellant/insulation layer interface more dangerous. When considering the damage at the interface,the stress near the root of the artificial debonding layer increases first and then decreases with the increase of the inflation pressure. In the process of increasing the internal pressure of inflation,when considering the interface damage between the propellant grain and the thermal insulation layer,the dangerous point of the propellant grain changes from the position near the root of the artificial debonding layer to the initial point perpendicular to the axial direction.
作者
陈科
任全彬
王健儒
刘琪琪
CHEN Ke;REN Quan-bin;WANG Jian-ru;LIU Qi-qi(School of Astronautics,Northwestern Polytechnical University,Xi’an 710072,China;Xi’an Aerospace Power Technology Research Institute,Xi’an 710025,China;School of Aerospace Engineering,Xi’an Jiaotong University,Xi’an 710049,China)
出处
《推进技术》
EI
CAS
CSCD
北大核心
2022年第10期342-350,共9页
Journal of Propulsion Technology
关键词
立式贮存
粘接界面
粘接接触
充气内压
药柱完整性
Vertical storage
Adhesive interface
Adhesive contact
Internal inflation pressure
Grain integrity
